CN103847975A - Embedding type airborne photoelectric turret and aircraft - Google Patents
Embedding type airborne photoelectric turret and aircraft Download PDFInfo
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- CN103847975A CN103847975A CN201410103099.8A CN201410103099A CN103847975A CN 103847975 A CN103847975 A CN 103847975A CN 201410103099 A CN201410103099 A CN 201410103099A CN 103847975 A CN103847975 A CN 103847975A
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- catadioptre
- capstan head
- airborne photoelectric
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Abstract
The invention provides an embedding type airborne photoelectric turret and an aircraft. The interior of the embedding type airborne photoelectric turret comprises a first system (17), a second system (18) and a center coupling lens (2). After the light reaches the center coupling lens (2), one part of light enters the first system (17) via a through hole (21), the other part of light is reflected by the center coupling lens (2) and enters the second system (18), and the different optical systems are coupled into one optic channel, so the coaxial and channel-sharing effects are realized, and the two optical windows of the prior art are changed into one optical window. The aircraft containing the embedding type airborne photoelectric turret has good pneumatic performance, maneuvering performance, structure performance and safety performance.
Description
Technical field
The present invention relates to airborne opto-electronic device technical field, concrete is a kind of inserted airborne photoelectric capstan head, or a kind of aircraft that contains this inserted airborne photoelectric capstan head.
Background technology
Existing airborne photoelectric capstan head can be divided into external hanging type capstan head and the large class of Integral turning tower two.Wherein external hanging type airborne photoelectric capstan head is divided into control part two bodies in plug-in capstan head part and cabin conventionally, and the factor of the aspects such as the volume of plug-in capstan head part, weight, structural strength and planform all can produce larger adverse effect for aeroperformance, maneuvering performance, structural behaviour and the safety performance etc. of aircraft.So-called integral type airborne photoelectric capstan head is by entirety of all component integrations, be mounted on airframe outside face, or the head of capstan head is stretched outside fuselage, within other parts are positioned at fuselage, so just can reduce structural volume and the impact of weight on aircraft of fuselage outside, but existing capstan head is common or have two optical windows, or adopt super semisphere optical window mouth mirror.
, no matter be external hanging type capstan head or Integral turning tower, all there is weak point separately in existing airborne photoelectric capstan head.Wherein be hung on the volume and weight of part outside airframe because it is outer larger for external hanging type capstan head, thereby aeroperformance, maneuvering performance, structural behaviour and safety performance etc. to aircraft all can produce very large adverse effect.And Integral turning tower or cause outside machine partial volume larger because thering are two optical windows, or in order to realize the operating range in its hemisphere spatial domain, also need to adopt one and be worth high super semisphere optical window mouth mirror.Because aircraft flight speed is fast and frequent landing, ground and the aerial foreign material such as dust, sandstone very easily pollute and damage super semisphere optical window mouth mirror.
Summary of the invention
There are two awkward technical matterss of optical window in order to solve Integral turning tower in prior art.The invention provides a kind of inserted airborne photoelectric capstan head and a kind of aircraft, this inserted airborne photoelectric capstan head, neither there is the plug-in part of fuselage, do not need to offer two optical windows yet, more do not need to adopt to be worth highly and subject to stained super semisphere optical window mouth mirror, can make above-mentioned external-hanging structure form problem, volume weight problem, the super hemisphere optical window that affects aircraft aeroperformance, maneuvering performance, structural behaviour, safety performance be worth costliness and subject to stained problem etc. to be solved in the lump.
The present invention is that the technical scheme that solves its technical matters employing is: a kind of inserted airborne photoelectric capstan head, comprises capstan head body and the fairing that is arranged on capstan head body bottom; Described inserted airborne photoelectric capstan head contains the first system, second system and central coupling mirror, central authorities' coupling mirror is arranged between the camera lens of the first system and the camera lens of second system, in central authorities' coupling mirror, be provided with through hole, light can enter described inserted airborne photoelectric capstan head and arrive central coupling mirror from the window of bottom part of fairing, part light enters the first system from through hole, and another light enters second system through the reflection of central coupling mirror.
The first system and second system are all arranged in capstan head body, and the angle of central coupling mirror and optical axis is 45 °.
The surface of central authorities' coupling mirror is coated with total reflection film, and the through hole in central coupling mirror is track type.
Described inserted airborne photoelectric capstan head contains the first catadioptre, the second catadioptre, the 3rd catadioptre and the 4th catadioptre, the first catadioptre is parallel with the second catadioptre, the 3rd catadioptre is parallel with the 4th catadioptre, angle between the second catadioptre and the 3rd catadioptre is 90 °, and the angle between the 4th catadioptre and central coupling mirror is 90 °; Light can enter described inserted airborne photoelectric capstan head also successively through extremely central coupling mirror of the first catadioptre, the second catadioptre, the 3rd catadioptre and the 4th catadioptre back reflection from the window of bottom part of fairing.
Fairing contains pitching swing type mechanism, this pitching swing type mechanism comprises pitching mirror unit for the first catadioptre is installed and the pitching motor for driving the first catadioptre to rotate, and this pitching motor can drive the first catadioptre to rotate as axle through the optical axis of the first catadioptre take horizontal direction.
This pitching swing type mechanism comprises hollow axis of revolution, and hollow axis of revolution is tubular, and the first catadioptre and pitching mirror unit are arranged in hollow axis of revolution, and described pitching motor can drive the first catadioptre, pitching mirror unit and hollow axis of revolution together to rotate.
The barrel of hollow axis of revolution is provided with the plane optics window mirror corresponding with window, and light can pass window and plane optical window mirror successively to the first catadioptre.
Fairing contains orientation swing type mechanism, this orientation swing type mechanism comprises the orientation mirror unit for the second catadioptre, the 3rd catadioptre and the 4th catadioptre are installed, this orientation swing type mechanism also comprises azimuth motor, and this azimuth motor can drive the second catadioptre, the 3rd catadioptre, the 4th catadioptre and described pitching swing type mechanism on orientation mirror unit together to rotate as axle through the optical axis of central coupling mirror take vertical direction.
The bottom of fairing be shaped as spherical crown, the height of this spherical crown is less than the radius of this spherical crown place spheroid.
A kind of aircraft, this aircraft contains above-mentioned inserted airborne photoelectric capstan head, and the capstan head body of this inserted airborne photoelectric capstan head is arranged in this aircraft, and the bottom-exposed of fairing is outside the wallboard of this aircraft.
The invention has the beneficial effects as follows:
1, the inserted airborne photoelectric capstan head in the present invention comprises the inside and outside two parts of fuselage, machine outside is divided into movable part, by 360 ° of revolutions and above it can ± optical window of 90 ° of pitching realizes hemisphere spatial domain operating range, in machine, part can require flexible combination according to function and space by central coupling mirror.
2, the inserted airborne photoelectric capstan head in the present invention only has a plane optical window, and can in the time not working, forward concealed location in order to avoid tarnish.
3, the inserted airborne photoelectric capstan head in the present invention, being shaped as spherical crown, being highly less than the radius of this spherical crown place spheroid of the outer rotating part of machine, revolution is steadily, aeroperformance is good, little on the impact of aircraft.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, inserted airborne photoelectric capstan head of the present invention is described in further detail.
Fig. 1 is the structural representation of this inserted airborne photoelectric capstan head.
Fig. 2 is the schematic diagram of central coupling mirror.
Wherein 1. capstan head bodies, 2. central coupling mirror, 3. the first catadioptre, 4. pitching mirror unit, 5. plane optics window mirror, 6. hollow axis of revolution, 7. bearing, 8. bearing seat, 9. pitch reference, 10. transmission device, 11. control circuits, 121. second catadioptres, 122. the 3rd catadioptres, 123. the 4th catadioptres, 13. orientation mirror units, 14. hollow bearings, 15. azimuth sensors, 16. fairings, 17. the first systems, 18. second systems, 19. windows, 20. wallboards, 21. through holes, 22. transmission devices.
The specific embodiment
Below in conjunction with accompanying drawing, inserted airborne photoelectric capstan head of the present invention is described in further detail.A kind of inserted airborne photoelectric capstan head, comprises capstan head body 1 and the fairing 16 that is arranged on capstan head body 1 bottom; Described inserted airborne photoelectric capstan head contains the first system 17, second system 18 and central coupling mirror 2, central authorities' coupling mirror 2 is arranged between the camera lens of the first system 17 belows and the camera lens on second system 18 right sides, in central authorities' coupling mirror 2, be provided with through hole 21, optical signal can enter described inserted airborne photoelectric capstan head and arrive central coupling mirror 2 from the window 19 of fairing 16 bottoms, part optical signal enters the first system 17 from through hole 21, another optical signal enters second system 18 through the reflection of central coupling mirror 2, as depicted in figs. 1 and 2.
Capstan head body 1 can be made up of aluminum alloy or other materials, for the installation between inserted airborne photoelectric capstan head and aircraft wallboard fix, position between the inner each function parts of capstan head is fixing etc.Central authorities' coupling mirror 2 can be made up of ordinary optical glass, quartzy optical glass or other materials, realize different pedigree reflection of lights, transmission, light splitting, close the functional requirements such as light by polishing, plated film or other technique, and be placed in 45° angle on the optical axis of the optical channel shown in long and short dash line in Fig. 1, such as, for different optical system (viewing optical system, measurement optical system etc.) is coupled to same optical channel, thereby realize coaxial and common road.Change two optical windows of prior art into one thereby realized.
As shown in Figure 1, the first system 17 and second system 18 are all arranged in capstan head body 1, and central coupling mirror 2 is 45 ° with the angle of top optical axis.Central authorities' coupling mirror 2 is made up of K9 optical glass, on the driving surface after polishing, is coated with total reflection film, and the through hole 21 in central coupling mirror 2 is track type, as shown in Figure 2.The via design of this central authorities' coupling mirror 2 is that track type is that two ends half radius of a circle of this track type is 15mm in order to make it be projected as circle on level and vertical direction in Fig. 1, and the major axis of this track type is 43mm.
As shown in Figure 1, described inserted airborne photoelectric capstan head contains the first catadioptre 3, the second catadioptre 121, the 3rd catadioptre 122 and the 4th catadioptre 123, the first catadioptre 3 is parallel with the second catadioptre 121, the 3rd catadioptre 122 is parallel with the 4th catadioptre 123, angle between the second catadioptre 121 and the 3rd catadioptre 122 is 90 °, and the angle between the 4th catadioptre 122 and central coupling mirror 2 is 90 °; As shown in the direction of arrow in Fig. 1, light can enter described inserted airborne photoelectric capstan head also successively through extremely central coupling mirror 2 of the first catadioptre 3, the second catadioptre 121, the 3rd catadioptre 122 and the 4th catadioptre 123 back reflections from the window 19 of fairing 16 bottoms, then a part of light enters the first system 17 from through hole 21, and another light enters second system 18 through the reflection of central coupling mirror 2.
In order to realize the hemisphere spatial domain operating range of this inserted airborne photoelectric capstan head, fairing 16 contains pitching swing type mechanism, this pitching swing type mechanism comprises the pitching mirror unit 4 for the first catadioptre 3 is installed and the pitching motor for driving the first catadioptre 3 to rotate, and this pitching motor can drive the optical axis ° rotation as axle ± 90 through the first catadioptre 3 take horizontal direction of the first catadioptre 3.This pitching swing type mechanism also comprises hollow axis of revolution 6, hollow axis of revolution 6 is tubular, the first catadioptre 3 and pitching mirror unit 4 are arranged in hollow axis of revolution 6, and described pitching motor can drive the together optical axis ° rotation as axle ± 90 through the first catadioptre 3 take horizontal direction of the first catadioptre 3, pitching mirror unit 4 and hollow axis of revolution 6.
The barrel of hollow axis of revolution 6 is provided with the plane optics window mirror 5 corresponding with window 19, and light can pass window 19 and plane optical window mirror 5 directive the first catadioptres 3 successively.Plane optics window mirror 5 can be with logical rotation of hollow axis of revolution 6 one, and plane optics window mirror 5 can forward concealed location in order to avoid tarnish in the time not working like this.As shown in Figure 1, this pitching swing type mechanism also comprises bearing 7, bearing seat 8, pitch reference 9, transmission device 10 and control circuit 11.
In order to realize the hemisphere spatial domain operating range of this inserted airborne photoelectric capstan head, fairing 16 contains orientation swing type mechanism, this orientation swing type mechanism comprises for the second catadioptre 121 is installed, the orientation mirror unit 13 of the 3rd catadioptre 122 and the 4th catadioptre 123, i.e. the second catadioptre 121, the position of the 3rd catadioptre 122 and the 4th catadioptre 123 is relative fixing, this orientation swing type mechanism also comprises azimuth motor, this azimuth motor can drive the second catadioptre 121 on orientation mirror unit 13, the 3rd catadioptre 122, the 4th catadioptre 123, the optical axis that pitching swing type mechanism and fairing 16 together pass through central coupling mirror 2 take vertical direction is as 360 ° of rotations of axle.This orientation swing type mechanism also comprises hollow bearing 14, azimuth sensor 15, transmission device 22 and control circuit 11.This control circuit 11 is arranged in capstan head body 1.
Due to only reversible, the first system 17 can be optical signal transmitting or receiving system, the clear aperture of the first system 17 is 20mm, second system 18 can be also optical signal transmitting or receiving system, the clear aperture of second system 18 is 80mm, existing be optical signal receiving system take the first system 17 and second system 18 and introduce the working process of this inserted airborne photoelectric capstan head as example.As shown in Figure 1, light passes through plane optics window mirror 5, the first catadioptre 3, the second catadioptre 121, the 3rd catadioptre 122, the central coupling mirror 2 of the rear arrival of the 4th catadioptre 124 successively by the direction of arrow, then a part of light enters the first system 17 from through hole 21, and another light enters second system 18 through the reflection of central coupling mirror 2.The first catadioptre 3 can the optical axis ° rotation as axle ± 90 through the first catadioptre 3 take horizontal direction, for realize optical channel ± 90 ° of pitching scannings; The optical axis that the first catadioptre 3, the second catadioptre 121, the 3rd catadioptre 122 and the 4th catadioptre 123 can together pass through central coupling mirror 2 take vertical direction is as 360 ° of rotations of axle, for realizing the n × 360 ° azimuth sweep of optical channel.
A kind of aircraft, this aircraft contains above-mentioned inserted airborne photoelectric capstan head, as shown in Figure 1, the capstan head body 1 of this inserted airborne photoelectric capstan head is arranged in this aircraft, capstan head body 1 is fixedly connected with the wallboard 20 of this aircraft, only has the spherical bottom-exposed of fairing 16 outside the wallboard 20 of this aircraft.
The above, be only specific embodiments of the invention, can not limit the scope that invention is implemented with it, thus the displacement of its equivalent assemblies, or equivalent variations and the modification done according to scope of patent protection of the present invention, all should still belong to the category that this patent is contained.Between technical scheme and technical scheme, all can use by independent assortment in addition, between the technical characterictic and technical characterictic in the present invention, between technical characterictic and technical scheme.
Claims (10)
1. an inserted airborne photoelectric capstan head, is characterized in that, described inserted airborne photoelectric capstan head comprises capstan head body (1) and is arranged on the fairing (16) of capstan head body (1) bottom;
Described inserted airborne photoelectric capstan head contains the first system (17), second system (18) and central coupling mirror (2), central authorities' coupling mirrors (2) are arranged between the camera lens of the first system (17) and the camera lens of second system (18), in central authorities' coupling mirrors (2), be provided with through hole (21), light can enter described inserted airborne photoelectric capstan head and arrive central coupling mirror (2) from the window (19) of fairing (16) bottom, part light enters the first system (17) from through hole (21), another light enters second system (18) through the reflection of central coupling mirror (2).
2. inserted airborne photoelectric capstan head according to claim 1, is characterized in that: the first system (17) and second system (18) are all arranged in capstan head body (1), and central coupling mirror (2) is 45 ° with the angle of optical axis.
3. inserted airborne photoelectric capstan head according to claim 2, is characterized in that: the surface of central coupling mirror (2) is coated with total reflection film, and the through hole (21) in central coupling mirror (2) is track type.
4. inserted airborne photoelectric capstan head according to claim 2, it is characterized in that: described inserted airborne photoelectric capstan head contains the first catadioptre (3), the second catadioptre (121), the 3rd catadioptre (122) and the 4th catadioptre (123), the first catadioptre (3) is parallel with the second catadioptre (121), the 3rd catadioptre (122) is parallel with the 4th catadioptre (123), angle between the second catadioptre (121) and the 3rd catadioptre (122) is 90 °, and the angle between the 4th catadioptre (123) and central coupling mirror (2) is 90 °;
Light can enter described inserted airborne photoelectric capstan head also successively through extremely central coupling mirror (2) of the first catadioptre (3), the second catadioptre (121), the 3rd catadioptre (122) and the 4th catadioptre (123) back reflection from the window (19) of fairing (16) bottom.
5. inserted airborne photoelectric capstan head according to claim 4, it is characterized in that: fairing (16) contains pitching swing type mechanism, this pitching swing type mechanism comprises pitching mirror unit (4) for the first catadioptre (3) is installed and the pitching motor for driving the first catadioptre (3) to rotate, and this pitching motor can drive the first catadioptre (3) to rotate as axle through the optical axis of the first catadioptre (3) take horizontal direction.
6. inserted airborne photoelectric capstan head according to claim 5, it is characterized in that: this pitching swing type mechanism comprises hollow axis of revolution (6), hollow axis of revolution (6) is tubular, the first catadioptre (3) and pitching mirror unit (4) are arranged in hollow axis of revolution (6), and described pitching motor can drive the first catadioptre (3), pitching mirror unit (4) and hollow axis of revolution (6) together to rotate.
7. inserted airborne photoelectric capstan head according to claim 6, it is characterized in that: the barrel of hollow axis of revolution (6) is provided with the plane optics window mirror (5) corresponding with window (19), light can pass window (19) and plane optical window mirror (5) directive the first catadioptre (3) successively.
8. inserted airborne photoelectric capstan head according to claim 5, it is characterized in that: fairing (16) contains orientation swing type mechanism, this orientation swing type mechanism comprises for the second catadioptre (121) is installed, the orientation mirror unit (13) of the 3rd catadioptre (122) and the 4th catadioptre (123), this orientation swing type mechanism also comprises azimuth motor, this azimuth motor can drive the second catadioptre (121) on orientation mirror unit (13), the 3rd catadioptre (122), the optical axis that the 4th catadioptre (123) and described pitching swing type mechanism together pass through central coupling mirror (2) take vertical direction is as axle rotation.
9. inserted airborne photoelectric capstan head according to claim 1, is characterized in that: the bottom of fairing (16) be shaped as spherical crown, the height of this spherical crown is less than the radius of this spherical crown place spheroid.
10. an aircraft, it is characterized in that: this aircraft contains the inserted airborne photoelectric capstan head described in any one in claim 1～9, the capstan head body (1) of this inserted airborne photoelectric capstan head is arranged in this aircraft, and the bottom-exposed of fairing (16) is outside the wallboard (20) of this aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410103099.8A CN103847975B (en) | 2014-03-19 | 2014-03-19 | A kind of inserted airborne photoelectric capstan head and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410103099.8A CN103847975B (en) | 2014-03-19 | 2014-03-19 | A kind of inserted airborne photoelectric capstan head and aircraft |
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| CN103847975A true CN103847975A (en) | 2014-06-11 |
| CN103847975B CN103847975B (en) | 2016-07-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410103099.8A Active CN103847975B (en) | 2014-03-19 | 2014-03-19 | A kind of inserted airborne photoelectric capstan head and aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105484616A (en) * | 2015-12-07 | 2016-04-13 | 中国航空工业集团公司洛阳电光设备研究所 | Rotary tower light window |
| CN105700131A (en) * | 2016-04-13 | 2016-06-22 | 北醒（北京）光子科技有限公司 | Rear-view optical scanning mirror set and scanning device |
| CN110068923A (en) * | 2019-04-24 | 2019-07-30 | 合肥鑫晟光电科技有限公司 | Dimming device, control method thereof and display system |
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| US4729071A (en) * | 1986-11-03 | 1988-03-01 | Altman Stage Lighting Co. | Low-inertial beam direction lighting system |
| US5696637A (en) * | 1994-08-08 | 1997-12-09 | Reliance Electric Industrial Company | Apparatus for positioning an optical line of sight within a hemispheric region |
| US20070152099A1 (en) * | 2003-12-12 | 2007-07-05 | Dominique Moreau | Onboard modular optronic system |
| CN101860684A (en) * | 2010-06-21 | 2010-10-13 | 福建福光数码科技有限公司 | Airborne turret with in-built CCD camera and forward looking infrared device and control system thereof |
| CN203259248U (en) * | 2013-03-07 | 2013-10-30 | 中国计量学院 | Portable colorimeter |
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2014
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4729071A (en) * | 1986-11-03 | 1988-03-01 | Altman Stage Lighting Co. | Low-inertial beam direction lighting system |
| US5696637A (en) * | 1994-08-08 | 1997-12-09 | Reliance Electric Industrial Company | Apparatus for positioning an optical line of sight within a hemispheric region |
| US20070152099A1 (en) * | 2003-12-12 | 2007-07-05 | Dominique Moreau | Onboard modular optronic system |
| CN101860684A (en) * | 2010-06-21 | 2010-10-13 | 福建福光数码科技有限公司 | Airborne turret with in-built CCD camera and forward looking infrared device and control system thereof |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105484616A (en) * | 2015-12-07 | 2016-04-13 | 中国航空工业集团公司洛阳电光设备研究所 | Rotary tower light window |
| CN105484616B (en) * | 2015-12-07 | 2017-11-14 | 中国航空工业集团公司洛阳电光设备研究所 | A kind of capstan head optical window |
| CN105700131A (en) * | 2016-04-13 | 2016-06-22 | 北醒（北京）光子科技有限公司 | Rear-view optical scanning mirror set and scanning device |
| CN105700131B (en) * | 2016-04-13 | 2017-12-19 | 北醒（北京）光子科技有限公司 | A kind of backsight optical scanner for robot |
| CN110068923A (en) * | 2019-04-24 | 2019-07-30 | 合肥鑫晟光电科技有限公司 | Dimming device, control method thereof and display system |
| CN110068923B (en) * | 2019-04-24 | 2022-05-13 | 合肥鑫晟光电科技有限公司 | Dimming device, control method thereof and display system |
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|---|---|
| CN103847975B (en) | 2016-07-27 |
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Address after: 100024 North East military villa, eight Li bridge, Chaoyang District, Beijing Patentee after: China Institute of Aeronautical Manufacturing Technology Address before: 100024 North East military villa, eight Li bridge, Chaoyang District, Beijing Patentee before: Beijing Aviation Manufacturing Engineering Institute of China Aviation Industry Group Company |